Double-layer rectifying blade structure of aero-engine

Abstract

The aero-engine double-layer rectifying blade structure comprises a blade outer wall, a blade inner wall and a plurality of supporting structures, a clearance space is defined between the blade outer wall and the blade inner wall, and the supporting structures are connected between the blade outer wall and the blade inner wall; a plurality of turbulent flow structures are arranged on the first wall face of the inner wall of the blade, and the first wall face is the side wall face, opposite to the outer wall of the blade, of the inner wall of the blade. The number of layers of the rectifying blades is increased, the anti-radiation coatings are sprayed on the solid surfaces of the rectifying blades, in order to enhance the stability of the double-layer structure, the supporting structures are additionally arranged in the interlayer, and when secondary flow enters a channel between the rectifying blades and the supporting plate, the supporting structures of the double-layer structure and the protruding turbulent flow structures enhance the turbulent flow effect. And heat exchange can be enhanced.

Description

Technical Field

[0001] The utility model relates to the technical field of aero-engines, and particularly relates to a double-layer fairing vane structure of an aero-engine. Background Art

[0002] The fairing vane is a vane fixed on the casing to increase the static pressure of the air flow and rectify the air flow. The fairing vanes of existing aero-engines are mainly located at the inter-stage casing or the rear bearing casing. The fairing vanes are exposed to the high-temperature mainstream, and there are also components such as struts and pipelines inside. Due to the action of the high-temperature mainstream gas, the temperature of the fairing vane is much higher than that of other metal components. The large temperature difference brings a relatively obvious radiation effect, resulting in the increase of the temperature of the originally lower-temperature strut. When the wall temperature rises to the maximum service temperature of the metal material, there is a risk of overheating, which further affects the local strength of the engine. For the pipelines inside the strut, when the temperature exceeds the temperature limit of the lubricating oil in the pipe, there is a certain risk of fire. Therefore, ensuring that the temperatures of the strut and the pipeline are within the maximum service temperature range is related to the safety performance of the engine.

[0003] In the field of aero-engines, ensuring that components are within the maximum service temperature range of the metal material is related to the safe and stable operation of the engine. Particular attention should be paid to the components exposed to the high-temperature mainstream gas. Since the radiation effect in the high-temperature area cannot be ignored, taking the fairing vane as a typical component, because the mainstream gas volume is larger than that of the secondary flow cold air, the heat transfer of the high-temperature gas dominates. This means that the wall temperature of the fairing vane is much higher than that of other components in the secondary flow. When its temperature reaches stability, it has a non-negligible radiation effect on the strut nested therein. At this time, the heat transfer degree of the cold air between the strut and the fairing vane is equivalent to the radiation heat transfer level. In addition to heat conduction, the radiation heat also causes a temperature rise of the strut, further affecting the pipelines inside the strut. The change of the temperature gradient and the increase of the absolute value of the temperature will both affect the strength and deformation. Therefore, if we want to ensure that the temperature of the internal structure is within the safe range, we should try to weaken the influence brought by the high-temperature components.

[0004] In view of this, the inventor of the present application designed a double-layer fairing vane structure of an aero-engine in order to overcome the above technical problems. Summary of the Utility Model

[0005] The technical problem to be solved by the utility model is to overcome the defect that in the prior art, the fairing vane is exposed to the high-temperature mainstream, and there are also components such as struts and pipelines inside. Due to the action of the high-temperature mainstream gas, the temperature of the fairing vane is much higher than that of other metal components. The large temperature difference brings a relatively obvious radiation effect, resulting in the increase of the temperature of the originally lower-temperature strut, and to provide a double-layer fairing vane structure of an aero-engine.

[0006] The utility model solves the above technical problems through the following technical solutions:

[0007] The present utility model provides a double-layer fairing blade structure for an aeroengine, characterized in that the double-layer fairing blade structure comprises: a blade outer wall, a blade inner wall, and a plurality of support structures. A gap space is enclosed between the blade outer wall and the blade inner wall, and the support structures are connected between the blade outer wall and the blade inner wall. A plurality of flow disturbing structures are arranged on a first wall surface of the blade inner wall, and the first wall surface is a wall surface of the blade inner wall opposite to the blade outer wall.

[0008] According to one or more embodiments of the present utility model, the double-layer fairing blade structure further comprises a support plate, and the support plate is arranged in the space enclosed by the blade inner wall.

[0009] According to one or more embodiments of the present utility model, the flow disturbing structures are perpendicular to the first wall surface and protrude upward along the first wall surface.

[0010] According to one or more embodiments of the present utility model, the flow disturbing structures are protruding rib plates.

[0011] According to one or more embodiments of the present utility model, the protruding rib plates extend from one end face of the blade inner wall to the other end face.

[0012] According to one or more embodiments of the present utility model, the flow disturbing structures are flow disturbing columns.

[0013] According to one or more embodiments of the present utility model, the support structures are connecting plates.

[0014] According to one or more embodiments of the present utility model, the connecting plates are perpendicular to the first wall surface.

[0015] According to one or more embodiments of the present utility model, the surfaces of the blade outer wall and the blade inner wall have anti-radiation coatings.

[0016] The positive and progressive effects of the present utility model are as follows:

[0017] The double-layer fairing blade structure of the aeroengine of the present utility model has at least the following advantages:

[0018] First, when the air intake of the secondary flow cooling air is constant, the double-layer structure increases the flow path of the cooling air. Originally, there was a large flow domain between the fairing blade and the support plate, and after the double-layer structure, it is equivalent to distributing the original total amount to the middle of the grid. According to the heat transfer boundary formula for the annular channel calculation, when the cross-sectional area of the flow channel decreases, the heat transfer is enhanced, that is, the secondary flow cooling effect is enhanced, which is beneficial to the cooling of high-temperature components.

[0019] II. After adding the double-layer structure, it can be equivalently understood that a heat insulation plate is added between the original single-layer rectifying vane and the strut. Due to the increase in the spatial thermal resistance and surface thermal resistance of radiation, the radiant heat transferred from the outermost high-temperature wall surface to the strut surface is reduced, further restricting the temperature rise of the strut and the internal pipeline.

[0020] III. Adding an anti-radiation coating on the surface of the rectifying vane. Materials with low emissivity and high reflectivity can be mainly used. Adding an anti-radiation coating on the basis of the double-layer structure can be used as another effective means to reduce the radiant heat between solids.

[0021] IV. The setting of the supporting structure and the convex spoiler structure that play a supporting role can enhance the heat transfer between the high-temperature wall surface and the secondary flow cold air. After reducing the radiation heat source, assisted by enhanced convection, the cooling effect is more ensured. BRIEF DESCRIPTION OF THE DRAWINGS

[0022] The above-mentioned and other features, properties and advantages of the present utility model will become more obvious through the following description in conjunction with the drawings and embodiments. The same reference numerals in the drawings always represent the same features, where:

[0023] Figure 1 is a three-dimensional schematic diagram of the double-layer rectifying vane structure of the aero-engine of the present utility model.

[0024] Figure 2 is a partial schematic diagram of the double-layer rectifying vane structure of the aero-engine of the present utility model.

[0025] Figure 3a is a top view schematic diagram of the double-layer rectifying vane structure of the aero-engine of the present utility model.

[0026] Figure 3b is a left view schematic diagram of the double-layer rectifying vane structure of the aero-engine of the present utility model.

[0027] Figure 3c is a front view schematic diagram of the double-layer rectifying vane structure of the aero-engine of the present utility model.

[0028] Figure 4 is a flow path schematic diagram when the double-layer rectifying vane structure of the aero-engine of the present utility model is in use.

[0029] Figure 5 is a radiation equivalent network schematic diagram of the single-layer rectifying vane structure.

[0030] Figure 6 is a radiation equivalent network schematic diagram of the double-layer rectifying vane structure.

[0031]

REFERENCE MARKS

[0032] Outer wall of the vane 100

[0033] Clearance space 110

[0034] Inner wall of blade 200

[0035] First wall surface 210

[0036] Turbulence structure 220

[0037] Support structure 300

[0038] Strut 400

[0039] Outer wall of strut 410

[0040] First convective heat transfer resistance 11

[0041] First surface heat resistance 12

[0042] Second surface heat resistance 13

[0043] First space heat resistance 14

[0044] Second space heat resistance 15

[0045] Third space heat resistance 16 Detailed implementation manners

[0046] To make the above objects, features, and advantages of the present utility model more obvious and understandable, the following detailed description of the specific implementation manners of the present utility model will be given in conjunction with the accompanying drawings.

[0047] Now, embodiments of the present utility model will be described in detail with reference to the drawings. Now, preferred embodiments of the present utility model will be described in detail, and examples thereof are shown in the drawings. In any possible case, the same reference numerals will be used throughout all the drawings to represent the same or similar parts. In addition, although the terms used in the present utility model are selected from well-known and commonly used terms, some of the terms mentioned in the description of the present utility model may be selected by the applicant according to his or her judgment, and their detailed meanings are described in the relevant parts of the description herein. In addition, it is required to understand the present utility model not only through the actual terms used, but also through the meaning implied by each term.

[0048] As Figures 1 to 4 shown, the present utility model discloses a double-layer fairing blade structure for an aeroengine, and the double-layer fairing blade structure includes: an outer wall of the blade 100, an inner wall of the blade 200, and a plurality of support structures 300.

[0049] A gap space 110 is enclosed between the outer wall 100 and the inner wall 200 of the blade, and the support structure 300 is connected between the outer wall 100 and the inner wall 200 of the blade; a plurality of flow disturbing structures 220 are arranged on the first wall surface 210 of the inner wall 200 of the blade, and the first wall surface 210 is the side wall surface of the inner wall 200 of the blade opposite to the outer wall 100 of the blade.

[0050] The double-layer fairing blade structure of the aero-engine of the present utility model can avoid the influence of the radiation heating of the fairing blade in the mainstream on the interior. Starting from the perspective of isolating the radiation heat source, the original single-layer fairing blade form is changed to a double-layer structure, increasing its space radiation thermal resistance and surface radiation thermal resistance, so that the radiation heat reaching the internal structure is weakened layer by layer, achieving an effective radiation heat isolation effect. The design of the flow disturbing structure 220 on the inner wall 200 surface of the fairing blade can strengthen the heat transfer to a certain extent. In addition, combined with spraying an anti-radiation and heat-insulating coating, it further increases the radiation heat to the environment and reduces the radiation heat transferred between solids. Furthermore, the purpose of solving from the root cause is achieved, thereby ensuring that the internal support plate 400 and pipelines are within the normal working temperature range, improving the safety and stability of the engine operation.

[0051] As Figures 1 to 4 shown, as a preferred embodiment of the double-layer fairing blade structure of the aero-engine of the present utility model, the double-layer fairing blade structure further includes a support plate 400, and the support plate 400 is arranged in the space enclosed by the inner wall 200 of the blade.

[0052] As Figures 1 to 4 shown, as a preferred embodiment of the double-layer fairing blade structure of the aero-engine of the present utility model, the flow disturbing structure 220 is perpendicular to the first wall surface 210 and protrudes upward along the first wall surface 210.

[0053] As Figures 1 to 4 shown, as a preferred embodiment of the double-layer fairing blade structure of the aero-engine of the present utility model, the flow disturbing structure 220 is a protruding rib plate.

[0054] As Figures 1 to 4 shown, as a preferred embodiment of the double-layer fairing blade structure of the aero-engine of the present utility model, the protruding rib plate extends from one end surface to the other end surface of the inner wall 200 of the blade.

[0055] The protruding rib plate can significantly increase the turbulence degree of the fluid in the fairing blade channel, making the heat exchange between the fluid and the blade surface more sufficient, thereby generating an enhanced heat exchange effect and helping to reduce the blade temperature.

[0056] As Figures 1 to 4As shown, as a preferred embodiment of the double-layer fairing blade structure of the aero-engine of the present utility model, the flow disturbing structure 220 is a flow disturbing post.

[0057] The shape of the flow disturbing post is preferably cylindrical and elliptical. The flow disturbing post can generate a strong flow disturbing effect in the fluid channel, significantly increasing the turbulence intensity of the fluid. This enhanced turbulence contributes to the heat exchange between the fluid and the blade surface, improving the heat transfer efficiency.

[0058] As Figures 1 to 4 shown, as a preferred embodiment of the double-layer fairing blade structure of the aero-engine of the present utility model, the support structure 300 is a connecting plate.

[0059] As Figures 1 to 4 shown, as a preferred embodiment of the double-layer fairing blade structure of the aero-engine of the present utility model, the connecting plate is perpendicular to the first wall surface 210.

[0060] Since the double-layer fairing blade structure of the aero-engine of the present utility model has the support structure 300 and the protruding flow disturbing structure 220 connected between the outer wall 100 and the inner wall 200 of the blade, when the cold air flows through the sandwich space, the protruding flow disturbing structure 220 and the support structure 300 increase the heat transfer area, more effectively increasing the heat exchange with the surrounding medium.

[0061] The protruding flow disturbing structure 220 and the first wall surface 210 form an uneven structure, thus increasing the turbulence. The turbulence reduces the boundary layer thickness, thereby improving the fluid mixing degree and heat transfer efficiency.

[0062] In addition, the protruding flow disturbing structure 220 increases the heat transfer path, enabling more heat to come into contact with the fluid during the heat transfer process, which is more conducive to the convective heat transfer.

[0063] As Figures 1 to 4 shown, as a preferred embodiment of the double-layer fairing blade structure of the aero-engine of the present utility model, the outer wall 100 and the inner wall 200 of the blade have anti-radiation coatings.

[0064] Preferably, the anti-radiation coatings are sprayed on the surfaces of the outer wall 100 and the inner wall 200 of the blade. The anti-radiation coatings have the characteristics of low emissivity and high reflectivity, and further control the radiant heat transferred between solids.

[0065] The present utility model forms an effective combination effect of anti-radiation and enhanced convection by improving the multi-layer structure, combining the anti-radiation coatings and the flow disturbing structure, aiming to protect the struts and pipelines inside the fairing blades to operate within a reasonable temperature range, and solve a series of problems such as wall surface overheating and strength, escorting the safe and stable operation of the engine.

[0066] Figure 4 It is a schematic diagram of the flow path. Figure 4 In it, the arrow F represents the flow path of the mainstream high-temperature gas, and its temperature is represented as T f , and its heat transfer coefficient is represented as h. Figure 4 In it, C1 represents the flow path of the secondary flow cold air flowing through the gap space 110, and its temperature is represented as T C1 , and its heat transfer coefficient is represented as h1. Figure 4 In it, C2 represents the flow path of the secondary flow cold air flowing through the space enclosed by the inner wall 200 of the blade, and its temperature is represented as T C2 , and its heat transfer coefficient is represented as h2.

[0067] Figure 4 In it, the outer wall 100 of the blade is defined as the first surface SF1, its wall temperature is TW1, and the surface area of the first surface SF1 is S1; the inner wall 200 of the blade is defined as the second surface SF2, its wall temperature is TW2, and the surface area of the second surface SF2 is S2; the outer wall 410 of the strut is defined as the third surface SF3, its wall temperature is TW3, and the surface area of the third surface SF3 is S3.

[0068] Figure 5 It is a schematic diagram of the radiation equivalent network of the single-layer structure, Figure 6 It is a schematic diagram of the radiation equivalent network of the double-layer structure. In Figures 5 to 6 it, the resistance value of the convective heat transfer resistance is represented as 1 / hS, and the convective heat transfer resistance includes the first convective heat transfer resistance 11, etc.; the resistance value of the space resistance is represented as 1 / AX, and the space resistance includes the first space resistance 14, the second space resistance 15, the third space resistance 16, etc.; the resistance value of the surface resistance is represented as (1 - ε) / εA, and the surface resistance includes the first surface resistance 12 and the second surface resistance 13, etc.

[0069] For the node J3, the single-layer and double-layer equations can be listed respectively as follows:

[0070] Single layer:

[0071] Double layer:

[0072] Through the above equations and Figures 4 to 6It can be known that assuming the same input of the mainstream high-temperature heat source, in the single-layer structure, the first surface SF1 and the third surface SF3 are retained, and the convective heat transfer coefficient of the secondary flow is converted into an h2'. Between the effective radiation first surface SF1 and the third surface SF3, the double-layer structure increases the space thermal resistance and surface thermal resistance. And because h1 is greater than h2', the value of the effective radiation first surface SF1 in the double-layer structure is already smaller than that of the single-layer. If a coating with a low emissivity is added, through comprehensive comparison, it can be concluded that the radiant heat reaching the third surface SF3, that is, the radiant heat reaching the strut 400, decreases. That is, assuming that other variables in the two equations remain unchanged, J1 of the single layer > J1 of the double layer > J2 of the double layer, and A2 of the double layer < A1. The first term of the double layer in the equation is smaller than that of the single layer. Therefore, J3 of the double layer should be smaller than J3 of the single layer. So the structure proposed by the present invention can effectively protect the strut 400 and the internal pipeline components, ensuring the safe and stable operation of the engine components.

[0073] The double-layer fairing vane structure of the aero-engine of the present invention increases the number of fairing vanes, has a radiation-proof coating sprayed on the solid surface of the fairing vanes, and in order to enhance the stability of the double-layer structure, a support structure 300 is added in the interlayer. When the secondary flow enters the channel between the fairing vane and the strut 400, the support structure 300 and the convex turbulence structure 220 of the double-layer structure enhance the turbulence effect and can strengthen the heat transfer.

[0074] The structure of the present invention has the characteristics of both strengthening the secondary flow cooling and weakening the radiation effect, and can effectively avoid the over-temperature risk of the strut 400 and other pipeline structures to a certain extent, ensuring the safe and stable operation of the engine.

[0075] In summary, the double-layer fairing vane structure of the aero-engine of the present invention has the following many advantages:

[0076] First, when the air intake volume of the secondary flow cold air is certain, the double-layer structure increases the flow path of the cold air. Originally, there was a large flow domain between the fairing vane and the strut 400, and after doubling, it is equivalent to distributing the original total amount to the middle of the grille. According to the heat transfer boundary formula for calculating the annular channel, when the cross-sectional area of the flow channel decreases, the heat transfer is enhanced, that is, the secondary flow cooling effect is enhanced, which is beneficial to the cooling of high-temperature components.

[0077] Second, after adding the double-layer structure, it can be equivalently understood that a heat insulation board is added between the original single-layer fairing vane and the strut 400. Due to the increase in the space thermal resistance and surface thermal resistance of the radiation, the radiant heat transferred from the outermost high-temperature wall surface to the surface of the strut 400 decreases, further restricting the temperature rise of the strut 400 and the internal pipeline.

[0078] Third, adding a radiation-proof coating on the surface of the fairing vane, mainly materials with low emissivity and high reflectivity can be used. Adding a radiation-proof coating on the basis of the double-layer structure can be used as another effective means to reduce the radiant heat between solids.

[0079] IV. Support function: The arrangement of the support structure 300 and the convex spoiler structure 220 can enhance the heat transfer between the high-temperature wall surface and the secondary flow cold air. After reducing the radiation heat source, assisted by enhanced convection, the cooling effect is more ensured.

[0080] Although the specific implementation manners of the present utility model have been described above, those skilled in the art should understand that these are only examples. The protection scope of the present utility model is defined by the appended claims. Without departing from the principle and essence of the present utility model, those skilled in the art can make various changes or modifications to these implementation manners, but these changes and modifications all fall within the protection scope of the present utility model.

Claims

1. A double-layer fairing blade structure for an aeroengine, characterized in that, The double-layer rectifying vane structure includes: a vane outer wall, a vane inner wall, and a plurality of support structures. A gap space is formed between the vane outer wall and the vane inner wall, and the support structures are connected between the vane outer wall and the vane inner wall; a plurality of flow disturbing structures are arranged on a first wall surface of the vane inner wall, and the first wall surface is a side wall surface of the vane inner wall opposite to the vane outer wall.

2. The double-layer fairing blade structure of an aero-engine according to claim 1, characterized in that, The double-layer rectifying vane structure further includes a support plate, and the support plate is arranged in the space enclosed by the vane inner wall.

3. The double-layer fairing blade structure of an aeroengine according to claim 1, wherein, The flow disturbing structures are perpendicular to the first wall surface and protrude upward along the first wall surface.

4. The double-layer fairing blade structure of an aeroengine according to claim 3, characterized in that The flow disturbing structures are protruding rib plates.

5. The double-layer fairing blade structure of an aeroengine according to claim 4, characterized in that, The protruding rib plates extend from one end face of the vane inner wall to the other end face.

6. The double-layer fairing blade structure of an aeroengine according to claim 1, characterized in that, The flow disturbing structures are flow disturbing columns.

7. The double-layer fairing blade structure of an aeroengine according to claim 1, characterized in that, The support structure is a connecting plate.

8. The double-layer fairing blade structure of an aeroengine according to claim 7, characterized in that, The connecting plate is perpendicular to the first wall surface.

9. The double-layer fairing blade structure of an aeroengine according to claim 1, characterized in that The surfaces of the vane outer wall and the vane inner wall have radiation-proof coatings.

Images